发动机压气机叶片断裂故障分析与试验验证  

Fracture Fault Analysis and Test Verification of Engine Compressor Blades

作　　者：张再德 ZHANG Zai-de(AECC Hunan Powerplant Research Institute,Hunan Zhuzhou 412002,China)

机构地区：[1]中国航发湖南动力机械研究所

出　　处：《失效分析与预防》2019年第4期258-261,共4页Failure Analysis and Prevention

摘　　要：发动机工作过程中出现燃气温度偏高的异常现象,返厂试车过程中Ⅱ级、Ⅲ级压气机转子叶片发生断裂。通过分解检查和理化分析,确定各断裂叶片的断裂性质及首断件;从设计、制造、装配、使用方面对首断件断裂原因进行分析,并采用整机模拟燃气温度偏高试验和压气机叶片叶尖振幅测量试验对断裂原因进行验证。结果表明:Ⅱ级压气机部分转子叶片发生高周疲劳断裂,为首断件;发动机严重进气畸变状态下,燃气温度偏高,Ⅱ级转子叶片一阶弯曲振动应力过高;可调叶片角度不准确、非正常激励频率是导致压气机叶片断裂的原因。The abnormal phenomenon of higher gas temperature occurred during the process of engine operation,and the compressor rotor blades of stage II and III fractured during later testing.Through decomposition inspection and physical and chemical analysis,the fracture mode and the first failure one of the fractured blades were determined.The fracture cause of the first failure part was analyzed from the aspects of design,manufacturing,assembly and use.And then the fracture cause was verified by the simulation test of higher gas temperature of the whole machine and the measurement test of compressor blade tip amplitude.The results show that high-cycle fatigue fracture occurred to some rotor blades of stage II compressor,which are the first failure parts. There were higher gas temperature and greater first-order bending vibration stress on stage II compressor blades under severe intake distortion condition.Inaccurate angle of adjustable blades and abnormal excitation frequency are the fracture cause of compressor blades.

关 键 词：发动机 压气机叶片 断裂 故障分析 验证 

分 类 号：V232[航空宇航科学与技术—航空宇航推进理论与工程]